WO2004031656A1 - Turbine a gaz - Google Patents

Turbine a gaz Download PDF

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Publication number
WO2004031656A1
WO2004031656A1 PCT/EP2003/009703 EP0309703W WO2004031656A1 WO 2004031656 A1 WO2004031656 A1 WO 2004031656A1 EP 0309703 W EP0309703 W EP 0309703W WO 2004031656 A1 WO2004031656 A1 WO 2004031656A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustion chamber
coolant
gas turbine
tubes
turbine
Prior art date
Application number
PCT/EP2003/009703
Other languages
German (de)
English (en)
Inventor
Wilhelm Schulten
Paul-Heinz Jeppel
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US10/525,780 priority Critical patent/US20050247062A1/en
Priority to EP03798881A priority patent/EP1537363A1/fr
Priority to JP2004540568A priority patent/JP4181546B2/ja
Publication of WO2004031656A1 publication Critical patent/WO2004031656A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the invention relates to a gas turbine having a combustion chamber in which a fuel supplied is reacted with combustion air supplied to produce a working medium.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a number of burners, compressed air being supplied by an air compressor.
  • the combustion of the fuel creates a working medium under high pressure at a high temperature.
  • This working medium is fed into a turbine unit downstream of the respective burner, where it relaxes while working.
  • Each burner can be assigned a separate combustion chamber, the working medium flowing out of the combustion chambers being able to be brought together in front of or in the turbine unit.
  • the gas turbine can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burners open into a common, usually annular, combustion chamber.
  • a cooling system constructed in this way has the disadvantage that the construction of the combustion chamber and the cooling system is very complex.
  • the actual combustion chamber wall is a separate one on the outside
  • Cooling system which in turn must be attached from the outside, assigned.
  • the manufacturing process of such a combustion chamber can thus be very costly and labor-intensive, since many individual parts and joining processes are necessary for the production. This also leads to an increased susceptibility to errors during manufacture and operation in the gas turbine. Maintenance and repair work is also made more difficult by the complicated combustion chamber wall construction.
  • the invention is therefore based on the object of specifying a gas turbine which has a particularly high efficiency even with a simple construction.
  • the wall of the combustion chamber is formed from coolant tubes.
  • the invention is based on the consideration that the gas turbine should be designed to ensure particularly high efficiency for particularly high media temperatures. In order to keep the susceptibility to errors low, particularly reliable cooling of the thermally loaded components, in particular the combustion chamber, should be ensured. This can be achieved with comparatively little effort, in that the combustion chamber wall, on the one hand, is also designed to be coolable and, on the other hand, is constructed from molded parts which are kept relatively simple and flexible.
  • the peripheral wall of the combustion chamber or combustion chamber wall is suitably constructed from pipes.
  • cooling air is provided as the coolant, which, after passing through the coolant tubes, can be supplied to the combustion chamber as additional combustion air preheated as a result of the combustion chamber cooling.
  • the combustion chamber wall, the coolant tubes are advantageously made of cast material, in other words, each form a cast part.
  • Another advantage of this choice of material is that reliable thermal insulation is made possible in a particularly simple manner by providing a suitable coating of the cast material with a ceramic protective layer.
  • coolant tubes In order to keep the coolant tubes particularly insensitive to thermal stresses and thus particularly robust, they are designed in an advantageous embodiment with a trapezoidal cross section.
  • This cross-sectional shape has a particularly high thermal elasticity which, even when the individual circumferential segments of the respective tube are heated to very different degrees, only leads to low thermal stresses between cold and warmer regions of the tube, so that a long service life of the coolant pipes can be achieved.
  • the coolant tubes are expediently attached to carrier rings oriented in the circumferential direction of the combustion chamber. Due to their position and shape, these carrier rings determine the shape of the annular space of the combustion chamber formed by the coolant tubes. In the manner of a self-supporting structure, the production of a mechanically stable combustion chamber structure is made possible by using only a small number of further components in addition to the actual pipes.
  • the coolant tubes are expediently attached to the carrier rings by means of cooled screws.
  • the fastening of the coolant pipes by means of screws allows a particularly time-saving assembly or disassembly of one or more coolant pipes from the hot gas side, that is, without having to disassemble the combustion chamber.
  • the carrier rings are advantageously connected to one another by a number of longitudinal ribs in addition to the actual coolant tubes.
  • the carrier rings and longitudinal ribs are preferably welded together, so that the rings and ribs form a welded supporting body.
  • a particularly high degree of flexibility in shaping the combustion chamber which in particular allows flow conditions in the working medium to be taken into account in the combustion chamber, while at the same time having a sufficient length and
  • the shape of the coolant tubes can be guaranteed can be achieved by the cooling tubes expediently consisting of two or more tube segments connected to one another in their longitudinal direction.
  • the advantage of segmenting the pipes can be, in particular, that production-technical difficulties in producing coolant pipes from cast iron with a sufficient length and appropriate shape are avoided.
  • each segment preferably has an associated transition or connecting piece at its respective tube end.
  • the transition pieces are expediently designed for easy connection to one another.
  • the transition pieces are in particular selected such that segments can be connected by means of a plug connection. If there is a trapezoidal cross section of the coolant pipes, the cross section of the transition piece is expediently selected such that it changes to a circular cross section right up to the connection point or to the respective pipe segment end. Such a circular end cross-section particularly enables simple machining options for a precisely fitting connection with the adjoining pipe segment.
  • this cooling system has the advantage that it is integrated into the wall structure of the combustion chamber and therefore only requires a few additional parts for the construction of the cooling system.
  • this cooling system due to the comparatively straight discharge of the coolant, there is only a slight loss of coolant pressure. This has the advantage that a high efficiency of the turbine is also favored on the coolant side.
  • the heat input into the coolant is advantageously recovered for the actual energy conversion process in the gas turbine.
  • the cooling air heated during the combustion chamber cooling and used as a coolant is advantageously fed into the combustion chamber, the preheated cooling air being able to serve as exclusive or additional combustion air.
  • each coolant tube is preferably connected on the output side to a collecting space, which in turn is connected upstream of the combustion chamber on the air side.
  • the coolant can be mixed with the rest of the compressor mass flow via a throttle device and fed to the combustion process.
  • a more even flow can be achieved by advantageously assigning such a collecting space to each burner, with the same amount of cooling air or coolant flowing to each collecting space by design.
  • each burner is preferably connected to a collection space, each collection space being connected to the same number of coolant tubes.
  • This arrangement has the particular advantage that approximately the same amount of recirculated cooling air is fed to each burner.
  • the combustion chamber is designed as an annular combustion chamber, the combustion chamber therefore has a particularly uniform combustion process.
  • the advantages achieved by the invention are, in particular, that the design of the combustion chamber wall as a plurality of interconnected coolant tubes provided for the flow of a coolant, in particular cooling air, enables particularly reliable combustion chamber cooling with a simple structure.
  • the integration of the coolant pipes in a self-supporting combustion chamber structure, in particular by means of the carrier rings, also enables comparatively simple interchangeability of individual pipes requiring maintenance, but due to the flexibility that can be achieved via the pipe construction, replacement of existing combustion chamber structures in already existing gas turbines is also possible in a simple manner is.
  • the construction of the combustion chamber from pipes is comparatively stable and insensitive to vibrations of the combustion chamber wall, since the coolant pipes stiffen and solidify the annulus.
  • the basic flexibility in terms of shape and component selection achieved through the construction of the combustion chamber wall from tubular elements also allows, in particular, the attachment of probes or monitoring sensors for monitoring and / or diagnosis of the actual combustion process in the combustion chamber, in particular through the targeted use of specifically modified pipes allow, for example, the passage of suitable probes from the outside into the interior of the combustion chamber.
  • FIG. 1 shows a half section through a gas turbine
  • FIG. 2 shows in longitudinal section a segment of the combustion chamber of the gas turbine according to FIG. 1, and
  • FIGS. 3a to c each show a cross section of a section of the combustion chamber wall according to FIG. 2. Identical parts are provided with the same reference symbols in all the figures.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator (not shown) or a work machine.
  • the turbine 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 which is designed as an annular combustion chamber, is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements, not shown.
  • the turbine 6 has a number of rotatable rotor blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of stationary guide vanes 14, which are also attached to an inner casing 16 of the turbine 6 in a ring shape, with the formation of rows of guide vanes.
  • the blades 12 are used to drive the turbine shaft 8 by transfer of momentum from the working medium M flowing through the turbine 6.
  • the guide blades 14, serve to guide the flow of the working medium M between two successive rows of blades or rotor blades as seen in the flow direction of the working medium M.
  • a successive pair of a ring of guide vanes 14 or a row of guide vanes and a ring of rotor blades 12 or a row of rotor blades is also referred to as a turbine stage.
  • Each guide vane 14 has a platform 18, also referred to as a blade root, which is arranged as a wall element for fixing the respective guide vane 14 to the inner housing 16 of the turbine 6.
  • the platform 18 is a thermally comparatively heavily loaded component, which forms the outer boundary of a heating gas channel for the working medium M flowing through the turbine 6.
  • Each rotor blade 12 is fastened in an analogous manner to the turbine shaft 8 via a platform 20 which is also referred to as a blade root.
  • each guide ring 21 is arranged on the inner casing 16 of the turbine 6.
  • the outer surface of each guide ring 21 is likewise exposed to the hot working medium M flowing through the turbine 6 and is spaced in the radial direction from the outer end 22 of the rotor blade 12 lying opposite it by a gap.
  • the guide rings 21 arranged between adjacent guide vane rows serve in particular as cover elements which protect the inner wall 16 or other housing installation parts against thermal overloading by the hot working medium M flowing through the turbine 6.
  • the gas turbine 1 is designed for a comparatively high outlet temperature of the working medium M emerging from the combustion chamber 4 of approximately 1200 ° C. to 1500 ° C.
  • its essential components, in particular the combustion chamber 4 are designed to be coolable.
  • the combustion chamber wall 23 is designed as a tube construction and is constructed from a large number of coolant tubes 24 which are connected to one another in a gas-tight manner to form the combustion chamber wall 23.
  • the combustion chamber 4 is designed as a so-called annular combustion chamber, in which a plurality of burners 10 arranged in the circumferential direction around the turbine shaft 8 open into a common combustion chamber space.
  • the combustion chamber 4 is in its entirety as an annular
  • the combustion chamber 4 has an initial or inflow section into which the outlet of the respectively assigned burner 10 opens.
  • the cross section of the combustion chamber 4 then narrows, the resulting flow profile of the working medium M being taken into account in this area.
  • the combustion chamber 4 On the output side, the combustion chamber 4 has a curvature in longitudinal section, by means of which the outflow of the working medium M from the combustion chamber 4 is favored in a first rotor blade row, which is seen for a particularly high impulse and energy transfer to the downstream flow side.
  • the combustion chamber wall 23 is formed both in the outer region of the combustion chamber 4 and in the inner region thereof by coolant tubes 24, the longitudinal axis of which is essentially parallel to the flow direction of the working medium M in the interior of the
  • Combustion chamber 4 are aligned.
  • the coolant tubes 24 are made of cast material, which is selected in particular in view of the particularly high mechanical and thermal strength of the coolant tubes.
  • each coolant tube 24 is formed in the exemplary embodiment by a suitable combination of a plurality of successive tube segments 26.
  • the type and number of pipe segments 26 are chosen such that, on the one hand, with regard to the length and shape of each pipe segment 26 and with regard to the casting material used, a particularly high mechanical strength of each individual pipe segment 26 is ensured, while on the other hand the shape also in each case un - Taking into account the desired flow path for the working medium M is selected appropriately.
  • the comparatively strong local curvatures that may be desired can be provided in a particularly simple and reliable manner by the segmentation of the coolant tubes 24.
  • the coolant tubes 24 are also designed for particular strength, particularly with regard to locally varying thermal loads and the resulting thermal stresses.
  • the coolant tubes 24 and in particular the tube segments 26 forming them are essentially trapezoidal in cross-section, as is shown for the middle piece of a tube segment 26 in FIG. 3a.
  • the coolant tubes 24 have a comparatively longer inside 28 and a comparatively shorter outside 30 in cross section.
  • a suitable seal for example a brush seal seal 32, is provided for sealing the interspaces between adjacent coolant tubes 24, so that the suitable combination of the coolant tubes 24 results in a closed and sealed combustion chamber 4 on the gas side.
  • the trapezoidal design of the pipe cross sections favors in particular a flat design of the structure obtainable by joining adjacent coolant pipes 24, so that the closed expansion management of the combustion chamber 4 can be reached in a comparatively simple manner.
  • a connection which is particularly simple with regard to assembly or maintenance purposes, is provided between two tube segments 26 of each coolant tube 24 that follow one another on the coolant side.
  • successive tube segments 26 of a coolant tube 24 are connected to one another via an associated transition piece 34.
  • each tube segment 26 is essentially round in its cross-section in its end regions to form the respective transition piece 34, as shown in FIG. 3b.
  • the production of the coolant tubes 24 from cast material enables the respective transition piece 34 to be molded onto the respective tube segment 26 in a comparatively simple manner, with the actually trapezoidal cross section of the respective tube segment 26 being continuously transferred to the circular cross section provided at the end in the transition region.
  • the respective transition pieces 34 are shifted into the outer region of the combustion chamber 4 with regard to their central line and in comparison to the middle pieces of the respective pipe segments 26, so that under
  • the coolant tubes 24 are fastened to a number of common carrier rings 36 which, viewed in the longitudinal direction or in the flow direction of the working medium M, enclose the combustion chamber 4 formed from the actual coolant tubes 24 in a suitably selected spacing.
  • the respective coolant tubes 24 or the tube segments 26 forming these are on the carrier rings 36 via coolable screws 38 attached, as shown in the embodiment of Figure 3c.
  • the carrier rings 36 are connected to one another by longitudinal ribs oriented essentially in the longitudinal direction or in the flow direction of the working medium M.
  • the design of the combustion chamber 4 as a tubular construction makes it possible to apply a comparatively large amount of cooling air as coolant K to the combustion chamber wall 23 with only comparatively small pressure losses.
  • the coolant K emerging from the coolant tubes 24 is to be fed into the as exclusive or additional combustion air Combustion chamber 4 is provided.
  • a supply of the coolant K to the coolant pipes 24 is provided at their end assigned to the outlet of the combustion chamber 4.
  • the coolant K is fed to the coolant tubes 24 there, as can be seen in FIG. 2, via suitable inflow openings 42.
  • the inflow openings 42 are positioned with respect to their spatial alignment in such a way that in the outlet area of the combustion chamber 4 the impinging cooling of the respective pipe segment 26 takes place first due to the cooling air flowing in as coolant K. Subsequently, the coolant K is deflected within the respective pipe segment 26, and then the coolant K flows through the respective coolant pipe 24 in its longitudinal direction, the cooling taking place by contact of the coolant K with the respective pipe wall.
  • the respective burner 10 from the outlet area of the combustion chamber 4 to its confluence area, in which the respective burner 10 is also arranged.
  • the coolant K which is now heated or preheated by the continuous cooling of the respective coolant tube 24 flows out of the coolant tubes 24 and is then assigned to a respective downstream collecting space 46.
  • the coolant tubes 24 are connected on the output side to the respectively assigned burner 10 via this collecting space 46, so that the coolant K flowing out of the coolant tubes 24 can be used as combustion air in the respective burner 10.
  • the feeding of the respective burner 10 with combustion air can be provided exclusively via the coolant K flowing out of the coolant tubes 24 or also with additional combustion air which may be additionally required and is supplied externally.
  • the combustion chamber 4 is designed as an annular combustion chamber, it is usually advantageous to arrange the burners 10 as symmetrically as possible and consequently to set the flow conditions within the combustion chamber 4 as symmetrically as possible.
  • This principle is also taken into account in the gas turbine 1 on the coolant side, with in particular each burner 10 being assigned the same number of coolant tubes 24 on the combustion air side.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Turbine à gaz (1) qui comporte une chambre de combustion (4) dans laquelle sont introduits et mis en réaction un combustible et de l'air de combustion, pour la production d'un milieu de travail (M). L'objet de la présente invention est de fournir une turbine à gaz à structure particulièrement simple, pour un rendement comparativement élevé de l'installation. A cet effet, la chambre de combustion (4) peut être refroidie et est conçue sous forme de structure tubulaire, la paroi (23) de la chambre de combustion étant composée de tubes (24) pour fluide de refroidissement.
PCT/EP2003/009703 2002-09-13 2003-09-01 Turbine a gaz WO2004031656A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US10/525,780 US20050247062A1 (en) 2002-09-13 2003-09-01 Gas turbine
EP03798881A EP1537363A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz
JP2004540568A JP4181546B2 (ja) 2002-09-13 2003-09-01 ガスタービン

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP02020694.2 2002-09-13
EP02020694A EP1398569A1 (fr) 2002-09-13 2002-09-13 Turbine à gaz

Publications (1)

Publication Number Publication Date
WO2004031656A1 true WO2004031656A1 (fr) 2004-04-15

Family

ID=31725437

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2003/009703 WO2004031656A1 (fr) 2002-09-13 2003-09-01 Turbine a gaz

Country Status (5)

Country Link
US (1) US20050247062A1 (fr)
EP (2) EP1398569A1 (fr)
JP (1) JP4181546B2 (fr)
CN (1) CN100394110C (fr)
WO (1) WO2004031656A1 (fr)

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US8695989B2 (en) 2004-04-30 2014-04-15 Siemens Aktiengesellschaft Hot gas seal
GB2434199B (en) * 2006-01-14 2011-01-05 Alstom Technology Ltd Combustor liner with heat shield
EP1862740B1 (fr) * 2006-05-31 2015-09-16 Siemens Aktiengesellschaft Paroi de chambre de combustion
US8397512B2 (en) * 2008-08-25 2013-03-19 General Electric Company Flow device for turbine engine and method of assembling same
EP2405200A1 (fr) * 2010-07-05 2012-01-11 Siemens Aktiengesellschaft Appareil de combustion et moteur de turbine à gaz
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
DE102011083814A1 (de) * 2011-09-30 2013-04-04 Mtu Aero Engines Gmbh Segmentiertes Bauteil
US10422532B2 (en) 2013-08-01 2019-09-24 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
CN104454174A (zh) * 2014-10-13 2015-03-25 罗显平 一种提高燃气发动机动力输出功率的方法

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GB376974A (en) * 1930-09-02 1932-07-21 Bbc Brown Boveri & Cie Improvements in and relating to combustion chambers
FR980028A (fr) * 1942-06-18 1951-05-07 Regent Perfectionnements apportés aux chambres de combustion
DE1025915B (de) * 1953-07-03 1958-03-13 Still Fa Carl Gasbeheizter Roehrenerhitzer mit einem aus Rohren gebildeten selbsttragenden Feuerraum
US3398527A (en) * 1966-05-31 1968-08-27 Air Force Usa Corrugated wall radiation cooled combustion chamber
US5129447A (en) * 1991-05-20 1992-07-14 United Technologies Corporation Cooled bolting arrangement
DE4343332A1 (de) * 1993-12-20 1995-06-22 Abb Management Ag Vorrichtung zur Konvektivkühlung einer dichten Brennkammer
US5832718A (en) * 1995-12-19 1998-11-10 Daimler-Benz Aerospace Airbus Gmbh Combustion chamber especially for a gas turbine engine using hydrogen as fuel

Also Published As

Publication number Publication date
EP1537363A1 (fr) 2005-06-08
CN1682078A (zh) 2005-10-12
JP2005538310A (ja) 2005-12-15
CN100394110C (zh) 2008-06-11
EP1398569A1 (fr) 2004-03-17
JP4181546B2 (ja) 2008-11-19
US20050247062A1 (en) 2005-11-10

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